CN216301468U - Composite wing unmanned aerial vehicle screw location locking means - Google Patents
Composite wing unmanned aerial vehicle screw location locking means Download PDFInfo
- Publication number
- CN216301468U CN216301468U CN202122231056.6U CN202122231056U CN216301468U CN 216301468 U CN216301468 U CN 216301468U CN 202122231056 U CN202122231056 U CN 202122231056U CN 216301468 U CN216301468 U CN 216301468U
- Authority
- CN
- China
- Prior art keywords
- aerial vehicle
- unmanned aerial
- concave
- positioning
- rack
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Active
Links
Images
Landscapes
- Steering-Linkage Mechanisms And Four-Wheel Steering (AREA)
Abstract
The utility model discloses a composite wing unmanned aerial vehicle propeller positioning and locking device, and particularly relates to the field of aviation design. The device comprises a concave-convex disc and a positioning locking mechanism, wherein the concave-convex disc comprises a transition connecting piece and concave-convex teeth, the transition connecting piece comprises a fixed column and cylindrical platforms, cylindrical bosses are arranged on the cylindrical platforms, and a circular plate is arranged between the two cylindrical platforms; the positioning locking mechanism comprises a sleeve, a positioning locking pin and a rack, the positioning locking pin and the rack are both located in the sleeve, a buffer spring is connected between the positioning locking pin and the rack, concave and convex teeth are located on a motion track of the positioning locking pin, a gear is meshed on the rack, the gear is coaxially connected with an output shaft of an unmanned aerial vehicle steering engine, a steering engine mounting support is arranged on the unmanned aerial vehicle steering engine, and the steering engine mounting support is connected with the sleeve through bolts. By adopting the technical scheme, the problem that the propeller of the existing composite wing unmanned aerial vehicle is locked and fixed in the cruise flight stage is solved, and the composite wing unmanned aerial vehicle can be used for ensuring the stability of the composite wing unmanned aerial vehicle in the cruise flight stage.
Description
Technical Field
The utility model relates to the field of aerometers, in particular to a composite wing unmanned aerial vehicle propeller positioning and locking device.
Background
In recent years, composite wing drones have attracted much attention because they can take off vertically as do composite wing drones, and also can cruise at high speed and long endurance as do fixed wing drones. The composite wing unmanned aerial vehicle is an unmanned aerial vehicle combining a fixed wing and a rotor wing, and the rotor wing is adopted in the taking-off and landing stage, so that the problem that the fixed wing has high requirement on the field during taking-off and landing is simply and effectively solved; adopt the fixed wing at the stage of cruising, can compensate rotor unmanned aerial vehicle flight speed low, the journey is short, the time of flight is short and flight stability shortcoming such as not enough. However, when the composite wing drone flies in cruising mode, the propeller may rotate continuously along with the change of the airflow, which not only increases the flight resistance, but also affects the flight performance of the drone. Thus, during cruise flight, it is of great significance to lock the propeller in a fixed position.
At present, a propeller positioning and locking device for a composite wing unmanned aerial vehicle is not mature enough, and the key difficulty lies in how to make the device have low power consumption and high reliability as much as possible, and the propeller positioning and locking device can be repeatedly used for many times.
SUMMERY OF THE UTILITY MODEL
The utility model aims to provide a propeller positioning and locking device of a composite wing unmanned aerial vehicle, which solves the problem that a propeller of the existing composite wing unmanned aerial vehicle is locked and fixed in the cruise flight stage.
In order to achieve the purpose, the technical scheme of the utility model is as follows: a composite wing unmanned aerial vehicle propeller positioning and locking device comprises a concave-convex disc and a positioning and locking mechanism, wherein the concave-convex disc comprises a transition connecting piece and concave-convex teeth, the cross section of the transition connecting piece is in a shape like a Chinese character 'wang', the transition connecting piece comprises a fixing column with a hollow inner part and cylindrical platforms arranged at the upper end and the lower end of the fixing column, the cylindrical platform at the upper side is connected with a propeller, a cylindrical boss is arranged on the cylindrical platform at the upper side, a circular plate coated on the fixing column is arranged between the two cylindrical platforms, and the concave-convex teeth are connected to the circular plate through bolts; the positioning locking mechanism comprises a sleeve, a positioning locking pin and a rack, the sleeve is installed on a base of the unmanned aerial vehicle, the positioning locking pin and the rack are located in the sleeve, a buffer spring is connected between the positioning locking pin and the rack, concave and convex teeth are located on a motion track of the positioning locking pin, a gear is meshed on the rack, the gear is coaxially connected with an output shaft of an unmanned aerial vehicle steering engine, a steering engine mounting support is arranged on the unmanned aerial vehicle steering engine and is connected with the sleeve through bolts.
Furthermore, a plurality of through holes are formed in the circular plate in the circumferential direction, and reinforcing ribs fixedly connected to the fixed columns are arranged on the fixing plates between the adjacent through holes.
Through the arrangement, the weight of the scheme can be reduced by utilizing the through holes, and the flight performance of the unmanned aerial vehicle can be kept; meanwhile, the strength of the concave-convex disc can be ensured by means of the reinforcing ribs, and the stability of the scheme is improved.
Furthermore, the steering engine of the composite wing unmanned aerial vehicle adopts a power-off self-locking motor.
Compared with the prior art, the beneficial effect of this scheme:
1. this scheme is through the interact between location locking round pin and the concave-convex dish, can drive the screw easily, accurately reachs the expectation position to realize the locking.
2. If when the positioning locking mechanism is started, the propeller still is in a low-speed rotating state, collision energy can be effectively alleviated through the buffer spring between the positioning locking pin and the rack, and influences caused by rigid collision are reduced.
3. But this scheme adoption outage auto-lock steering wheel, the low power dissipation, and have the good reliability, advantage such as used repeatedly many times accords with the requirement in present aviation field.
Drawings
Fig. 1 is a schematic structural diagram of the present embodiment in an unlocked state;
FIG. 2 is a schematic structural diagram of the concave-convex disc of the present embodiment;
FIG. 3 is an isometric view of the transition piece of the present embodiment;
FIG. 4 is an isometric view of the concave-convex teeth of this embodiment;
FIG. 5 is an isometric view of the positioning locking mechanism (without the steering engine) of this embodiment;
FIG. 6 is a schematic view of the internal structure of the positioning and locking mechanism in this embodiment;
FIG. 7 is a schematic view showing the engagement of the gear and the rack in this embodiment;
fig. 8 is a schematic view of the connection between the steering engine and the rack in this embodiment.
Detailed Description
The present invention will be described in further detail below by way of specific embodiments:
reference numerals in the drawings of the specification include: concave-convex disc 1, base 2, location locking mechanism 3, sleeve pipe 4, rotor motor 5, screw 6, cylindric platform 7, first strengthening rib 8, concave-convex tooth 9, fixed column 10, circular slab 11, first auricle 12, hemisphere button head 13, rack 14, boss 15, second auricle 16, location locking round pin 17, buffer spring 18, gear 19, steering wheel 20, steering wheel installing support 21.
Examples
As shown in figures 1 to 8: the utility model provides a compound wing unmanned aerial vehicle screw location locking means, includes concave-convex dish 1 and location locking mechanism 3, concave-convex dish 1 includes that the cross sectional shape is transition connection spare and the unsmooth tooth 9 of "king" font. Transition connection spare includes inside hollow fixed column 10 and sets up the cylinder platform 7 at fixed column 10 upper and lower both ends, equal circumference distributes on two cylinder platforms 7 has six screw thread clearance holes, the cylinder platform 7 that is located the upside is in the same place with 6 bolted connections of screw, be located and be equipped with cylinder boss 15 on the cylinder platform 7 of upside, the cylinder platform 7 that is located the downside is connected with 5 bolted connections of rotor motor, cylinder boss 15, run through jointly on two cylinder platforms 7 and the fixed column 10 and have the through-hole that supplies 6 pivots of screw to pass through. Be equipped with the circular slab 11 of cladding on fixed column 10 between two circular truncated cone bases 7, be equipped with two recesses and two convex departments on unsmooth tooth 9, peripheral evenly distributed has a plurality of first auricles 12 in unsmooth tooth 9, and threaded hole is all opened at the center of every first auricle 12, and unsmooth tooth 9 passes through threaded hole bolted connection on circular slab 11. A plurality of through holes are circumferentially formed in the circular plate 11 and are triangular, first reinforcing ribs 8 welded to the fixing columns 10 are arranged on the fixing plates between the adjacent through holes, the outer edges of all the first reinforcing ribs 8 are connected with fixing rings together, and the fixing rings are provided with threaded holes corresponding to the first lug plates 12.
The positioning locking mechanism 3 comprises a sleeve 4, a positioning locking pin 17 and a rack 14, the sleeve 4 is square, three second lug plates 16 which are integrally formed are coated outside the sleeve 4, and a second reinforcing rib welded between each lug plate and the sleeve 4 is arranged between every two adjacent second lug plates 16. Two bosses 15 arranged at intervals are integrally formed on one side wall outside the sleeve 4, and the bosses 15 are connected with a mounting rack bolt of the steering engine 20. The second tab 16 is bolted to the base 2 of the drone. The positioning locking pin 17 and the rack 14 are both connected in the sleeve 4 in a sliding manner, and the positioning locking pin 17 and the rack 14 are both in clearance fit with the sleeve 4. The top of location locking round pin 17 is equipped with and is connected with buffer spring 18 between location locking round pin 17 and the rack 14 with unsmooth 9 matched with hemisphere button heads 13 of tooth, and unsmooth 9 tooth is located hemisphere button heads 13's movement track, and the meshing has gear 19 on the rack 14, and gear 19 coaxial coupling has the steering wheel 20 installing support of "L" shape on the steering wheel 20 of unmanned aerial vehicle on the output shaft of unmanned aerial vehicle steering wheel 20.
In this embodiment, the steering engine 20 of the compound-wing drone adopts a power-off self-locking motor.
The positioning and locking method of the positioning and locking device comprises the following steps:
s1, when the composite wing unmanned aerial vehicle finishes taking off and landing, the rotor motor 5 is closed through the flight controller;
s2, when the rotor motor 5 stops rotating or the rotating speed drops to a preset value, the steering engine 20 is started and controlled to be started through the flight controller, the steering engine 20 drives the gear 19 to rotate anticlockwise at the moment, and the gear 19 and the rack 14 are used for driving the positioning locking pin 17 and the hemispherical round head 13 to move upwards.
And S3, if the position of the propeller 6 at the moment is deviated from the expected position, the positioning locking pin 17 can be used for driving the concave-convex teeth 9 to rotate, and when the hemispherical round head 13 moves to the concave position on the concave-convex teeth 9, the positioning locking of the propeller 6 is realized.
The method of releasing the detent lock of the present embodiment is as follows:
starting the steering engine 20 through the flight controller and making it rotate clockwise to can make gear 19 drive rack 14 and move down, hemisphere button head 13, location locking round pin 17, buffer spring 18 and rack 14 move down together and progressively with unsmooth dish 1 phase separation this moment, treat to realize the unblock after hemisphere button head 13 is located unsmooth dish 1 outward, utilize flight control to close steering engine 20 this moment can.
The foregoing are merely examples of the present invention and common general knowledge of known specific structures and/or features of the schemes has not been described herein in any greater detail. It should be noted that, for those skilled in the art, without departing from the structure of the present invention, several changes and modifications can be made, which should also be regarded as the protection scope of the present invention, and these will not affect the effect of the implementation of the present invention and the practicability of the patent. The scope of the claims of the present application shall be determined by the contents of the claims, and the description of the embodiments and the like in the specification shall be used to explain the contents of the claims.
Claims (3)
1. The utility model provides a compound wing unmanned aerial vehicle screw location locking means which characterized in that: the novel propeller-driven aircraft engine is characterized by comprising a concave-convex disc and a positioning locking mechanism, wherein the concave-convex disc comprises a transition connecting piece and concave-convex teeth, the cross section of the transition connecting piece is in a shape like a Chinese character 'wang', the transition connecting piece comprises a fixed column and cylindrical platforms, the fixed column is hollow inside, the cylindrical platforms are arranged at the upper end and the lower end of the fixed column, the cylindrical platform at the upper side is connected with a propeller, a cylindrical boss is arranged on the cylindrical platform at the upper side, a circular plate coated on the fixed column is arranged between the two cylindrical platforms, and the concave-convex teeth are connected to the circular plate through bolts; the positioning locking mechanism comprises a sleeve, a positioning locking pin and a rack, the sleeve is installed on a base of the unmanned aerial vehicle, the positioning locking pin and the rack are located in the sleeve, a buffer spring is connected between the positioning locking pin and the rack, concave and convex teeth are located on a motion track of the positioning locking pin, a gear is meshed on the rack, the gear is coaxially connected with an output shaft of an unmanned aerial vehicle steering engine, a steering engine mounting support is arranged on the unmanned aerial vehicle steering engine and is connected with the sleeve through bolts.
2. The composite wing drone propeller positioning and locking device of claim 1, wherein: a plurality of through holes are formed in the circular plate in the circumferential direction, and reinforcing ribs fixedly connected to the fixed columns are arranged on the fixing plates between the adjacent through holes.
3. The composite wing drone propeller positioning and locking device of claim 1, wherein: the steering engine of the composite wing unmanned aerial vehicle adopts a power-off self-locking motor.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202122231056.6U CN216301468U (en) | 2021-09-15 | 2021-09-15 | Composite wing unmanned aerial vehicle screw location locking means |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202122231056.6U CN216301468U (en) | 2021-09-15 | 2021-09-15 | Composite wing unmanned aerial vehicle screw location locking means |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN216301468U true CN216301468U (en) | 2022-04-15 |
Family
ID=81111570
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202122231056.6U Active CN216301468U (en) | 2021-09-15 | 2021-09-15 | Composite wing unmanned aerial vehicle screw location locking means |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN216301468U (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113844649A (en) * | 2021-09-15 | 2021-12-28 | 中国空气动力研究与发展中心空天技术研究所 | Composite wing unmanned aerial vehicle propeller positioning and locking device and method |
-
2021
- 2021-09-15 CN CN202122231056.6U patent/CN216301468U/en active Active
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113844649A (en) * | 2021-09-15 | 2021-12-28 | 中国空气动力研究与发展中心空天技术研究所 | Composite wing unmanned aerial vehicle propeller positioning and locking device and method |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| US9193451B2 (en) | Aircraft using turbo-electric hybrid propulsion system for multi-mode operation | |
| US6402088B1 (en) | Passenger vehicle employing a circumferentially disposed rotatable thrust assembly | |
| CN205707297U (en) | Fixed-wing unmanned plane | |
| US8939393B2 (en) | Aircraft with integrated lift and propulsion system | |
| CN103979104B (en) | One can variant X-type wing vertical landing minute vehicle | |
| US8864062B2 (en) | Aircraft with integrated lift and propulsion system | |
| US9308989B2 (en) | Aircraft front landing gear and method of operating the same | |
| CN105882959A (en) | Aircraft capable of vertical takeoff | |
| CN216301468U (en) | Composite wing unmanned aerial vehicle screw location locking means | |
| US20090266941A1 (en) | Combination Spar and Trunnion Structure for a Tilt Rotor Aircraft | |
| CN106347663A (en) | Unmanned aerial vehicle with wing body and flying wing blended layout | |
| CN202783780U (en) | Annular blown flap ducted aerial vehicle | |
| CN104290906A (en) | Vertical take-off and landing aircraft | |
| CN102673780A (en) | Double-configuration aircraft | |
| US20190389571A1 (en) | Engine and rotatable proprotor configurations for a tiltrotor aircraft | |
| WO2023197568A1 (en) | Aircraft realizing vertical take-off and landing, and control method for aircraft realizing vertical take-off and landing | |
| CN109987223A (en) | A kind of new vertical landing unmanned plane coupling wing configuration | |
| US11148798B2 (en) | Engine and rotatable proprotor configurations for a tiltrotor aircraft | |
| CN109533319A (en) | A kind of tilting rotor unmanned vehicle structural system with the overlap joint wing | |
| CN102424111B (en) | Flexible saucer-shaped aircraft | |
| CN104058092A (en) | Vertical taking-off and landing type electric aircraft | |
| CN204548499U (en) | Modularization combined type many rotors hybrid power aircraft | |
| CN102267564A (en) | Tiltable main power system adopted for microminiature short-distance/vertically taking off and landing flyer | |
| CN113844649A (en) | Composite wing unmanned aerial vehicle propeller positioning and locking device and method | |
| CN106005401A (en) | Unmanned aerial vehicle tail tilting pair power mechanism |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| GR01 | Patent grant | ||
| GR01 | Patent grant |